High fidelity time domain for spacecraft emulation systems

Abstract

An emulation system includes a central time source generating a time reference and an emulated spacecraft control processor which contains an embedded processor that provides an emulated input/output interface to communicate simulated spacecraft data. The embedded processor processes the simulated spacecraft data and contains a real time clock engine having a real-time clock period. The system further has a first simulation that processes attitude control system data from the emulated spacecraft control processor to simulate an attitude control system of the spacecraft in real-time. The first simulation engine operative to produce sensor data for input to the emulated spacecraft control processor based on the simulated system dynamics and adjusts the real time clock period in response to the time reference.

Description

TECHNICAL FIELD[0001]The present invention relates generally to spacecraft simulation, and more particularly to a complete spacecraft simulation system that accommodates high fidelity time domain test applications.BACKGROUND ART[0002]The increasing size and complexity of various spacecraft and associated subsystems therefore have created a need for detailed validation and verification before deployment. Examples of spacecraft subsystems requiring validation and verification include: (i) multiprocessor-based systems which can have complex software architectures; (ii) fault detection, isolation and response systems providing extended autonomous operations; (iii) multiple-articulated payloads and multibody control; (iv) precision payload pointing systems with multiple interacting elements; and (v) sophisticated ground software for automated spacecraft operations.[0003]However, system-level ground testing to verify full system performance of a spacecraft and associated ground system can...

AI Technical Summary

Benefits of technology

[0008]It is an object of the present invention to provide a low-cost, high fideli

Problems solved by technology

However, system-level ground testing to verify full system performance of a spacecraft and associated ground system can be costly and/or inadequate.

Otherwise, the system under test may yield inaccurate results or become inoperative.

Known implementations of such systems require a substantial amount of effort to achieve some measure of time domain fidelity and must extrapolate test results to achieve some level of verification and validation.

The resulting simulation was a function of the operator's hand-eye coordination and subject to propagation delays and uncertainties within the operating system.

Some of these tuning mechanisms were automate

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